Airship



Nov. 6, 192.8;

Y R. G. DNALDSON `AIRSHIP Filed DISC., 4, 1926 4 sheets-sheet 1 man Nov.6,' 1928.

R. G. DONALDSON AIRSHIP 4 S-hvewsnw, 2

Nw. 6, 192s.

R. G. DONALDSON AIRSHIP 'Filled Dec. 4, 192e 4 sheets-Sheet" 3 aucun,

Nov. e, 192s.

R. G. DONALDSON msm? Fixed nec.. 4, 192e Patented Nov. 6, A1928.

'new non L e351 i ROY G. DONALDSON, OF GRESTLINE, OHIO @aniram*amenazaba f4, en. str-a1 1a. 152,762.

Iliis invention relatesI "to Iaircraft of l'tlie v' y generally in adownward direction,` and 'to providemeansassoeiated With the distribuneimporta t' ebject'ef the invention is Vto fp'iiovide-en 'aircraftWlilileli is adapted "to Vascend and descend-substaiitially ve'r'tieallyvaftertlie nia-nner offtlie helicopter type "of aircraft, blib embodyingprinciples" of` opera tion entirely difer'ent from vsuoli 'a vt'y'peofaircraft.

further lobject/is 'to provide; an aircraftof tle It`yp"`e' referred 'toivliereintli'e elevating and. 'Stemming acria's obtained with "ania'rled-'iiicreasefin prop'eller'eicienc A further objectr is 'toprovide `v`an Caircraft oftlie "type referred to wherein "a propellerrQtat'i'ng about horizontal employed, 'aiid the 'aircurr'tfs iinpelledt'liere'froniare 114k controlled in such a manner as to eiiect,A

either fa direct vertical sustaining getipt or conipos'ite 'sustainingand lon inal propelling aetion whereby 'tlie an rait is adapted to'ascend "and descend u vertiea'lly and 'which is adapted to belprop"elled lio'ri` hiaat-any ihren-gh meant A :furtl fr "object is `toprovide a Sub tanmuy homorit'ai body jtimfne'l having ineens' in tli'e'orward Y"end t'fliereoi' ini peiling air rearwardly into ltlie trnnel'aid topr de distributing means whereby he air "currents may becontrolled fn such fa inann'er 'as "to Yeffect a sustaining ;`actiona1`i`d a lioricontal propelling action. 'A further object is'to provideanlai'reiaft of the character j'ust rnen't'ioiied wherein thedistributing means referred 'to readily controllable for A)varying `Atheeffects of 'the air currents dischargedtherefrom Wliereby either vavertical sustair'iing` action or a coinposite sustaining faction "and:horizontal pio pollingactionlread'ilv jbe obtained.

A further object 1ste provide an 'a' craft Vof the jeli'ar'acterreferred to wherein the distril'o'uting nkeians is furtlie'r providedwith controllable means for varying' the distributio'n of air throughthe 'di'stributingY ,means 'to lvary the sustaining' action accordinl;i`to the distribution of weight carried by the aircraft. A l A n y. A;riirtle'r object is toprovide an aircraft einploying a v'substantially"horizontal body 4or tunnel lia-vinoine/ans `for inipelli'ng airrearwardly tleremto and to provide series of distributorssubstantiallyangul'arly. ai'- ran'gjed Within the `bfody and liavingglg'their upp'erends 4:arranged 'at progressively increasiheightsl towardlthe rear l"end "of the body to intercept anddistribute tlie'iinpelledair tors vfor discharging the impelled 'air subangie vtothe vertical. ik

y further object is to "provide an aircraft of the chara'erter j'ustreferred to wherein 's tntially vertically or rearwardly at an `the bodyis provided vv'ith 'laterally projecting sustaining 'pla-lies. and'vvvherein such planes are 'provided yvitli aileronsftdper- `init'thecraft readily to be balanced transversely. 1 .e t e ,Aurther object 1stoprovide an aircraft of the character referred to wherein. tlie body `isprovided beneath its .forward vend witlifaftransverse elevating plane cy'Otlier ,objects and 'advantages of the invention willbe'eoinelapparent during Vthe course Lof "tlier lfollowing description.

`In the drawings I have shown one enivbodiment ofthe invention. i. Inthiszshoivng,` p'lan View showing the cover- 'ing removed',A c

j Figure 1 is :Figure 21's ai central Ivertical longitudinal sectionalView,

Figiire 3 is a fragmentary fperspeetiveof or' the distributor controls,Figure isla. frontelevation, l ,i

4rgure 5 is 'a transversesection taken substantially .on line 5456iFigii're, 2, and,

Figure is a fragmentary: transverse seo tional view similar to 'Figure 5takenthrough the ailerons. i

Referring tothe dra-Wings itlienun'ieral 1`0 designates the bdyportionoftlie "apparatus tlie forward i'end of which is vvsubstantiallycircular as indicated at 11. supporting frainelQ is arrangedjatthe/forward end of tlie body 'and a Suitable inotor 13 is nounted `atthe upper endof Ithe traine and `is adapted 'to drive vra 'suitableypropeller 14, It will be noted vthat the body `10 yforins substantiallya tunnel, fand tlie rear endethereofv iscnrved don-'n wvardlyjas at 15.The body may 'be lor'nied o'f a yplurality of traine ineinbersl theupper ends of which are/semi-circular:as

indicated at 17 (seef Figure 155i.. andY these frainie members [may beformed of any Suita'b le material such. as duraluniin and jnaybe iliadeasiods, tubes, or the like. t The vframe nelnbers 16 extend transverselyofthe body, shown, andl in'ay beusuftalaly 4rbraced by longitudinaltraine ineinbeis v18. l K The.,levver portionfof, body' flares Dut-W'ardly on epposite VFsides s at 179 andtermi f scribed.

are arranged angularly*within` theV body..

nates in opposite longitudinally extending supporting, plane portions'Vindicated as a whole by the numeral 20. These lower portions of theapparatus are constructedy upon a suitable frame work 21 formedy offrame members similar to those kpreviously yde transverse frame members22 and longitudi-- nal frame members d.3. Theupper portion.

kof the body `l0, the flared-portions 19;and `the sustainingplaneportions 20jare covered with suit-able airplane covering material24 y as shown in'Figure 5, and this material preferably extendsdownwardly over the edges of the sustaining plane `as'indicated ait-125.l

i Beneath the'r forward end of the.apparatus, a transverse lifting plane2 6` l is provided.V

This plane extends throughout thefwidth of ythefforward end ofjtheapparatus as indicated in Figure t, and is preferably curved as clearlyshown in Figure 2. This plane is provided for effecting a lifting actionfor Athe,

forward end of the appartus asitiS moving longitudinally through thelair.

Theentir Ilower kport-ion of the' body and sustaining planesare open aslclearlyshown in Figure 2, and means are provided for disf-tributing`downwardly, downwardly and l.

rearwardly, or forwardlyl the fair impelled through thel body-or tunnel`l0. As shown in A*Figure 2, apluarality of distributors 27 Thesedistributors `are arrangedk to extend downwardly toward the rear. endofthe apparatus to defiect the i'mpelled air .insuch directi'on. Inorder atokpermit the distribuytors to intercept vproperproportions ofthe impelled air,.the upperedges thereof arearranged at vprogressivelyincreasing heights as shown inFigure 2. Thedistrbutorshave their lowerends ilaredy outwardlyas atA 28,

- continu ous *and thelower edges of thedistributoisV terminate at theouter edges of theiiared portion 19, thatI is, at lthefinner extremitiesof 'the sustainingplanesf2O whereby there is a surface providedsustaining throughout the .length -of the apparatus.

The distribution of airis adapted to be `controlled to vary the angle atwhich lthe air is discharged from the bottom of the apparatus. This4distribution may be elfected in` any desired manner,y .and inthepres'ent instance I have shown thelower extremities -of thedistributors as'constituting separate 'members 29 hinged kto rtheadyacent portions of the distributors asat 3().` The control members 29havetheir lower portions connectedby cables 3'1 which pass'aroundpulleys 32. Obviously movement of the cables longitudinally isadapted to vary the angles oflthecontrol members 29. s

Means alsolareprovided for varying the proportions of air delivered tothe forward.

and rear distributors .to control the sustaining action throughout the:length of the air The lower frame work inclukiles"v members 21.

craft. As shown in Figure 2, the upper extremities of several of thedistributors may be` prov.' ded with movablepoitions 33 hinged to theadjacent portions of the distributors as at 34. The extremities ofthemovable .members 33 also are connected by cables 35 whichy passaround pulleys 3G. y

,i A,lVleansgare Vprovided for effecting transverse stabilization ofthe'aircraft, and for this'puipose ailerons 37 are provided in thesustaining planesas clearlyshown y in Figures 1 andV 6. lThese aileronsare pivotally connectedas -at38 with certain ofthe frame These aileronsare adapted to be controlled in such a manner that elevation of oneAofthem is adapted to depress v,

theother so that aliftingactionzwillbe delivered to one side of theapparatus 'simul-y taneouslywith a depressingpaction at the Elevators 39are pivotallyk opposite side; connected as at LlO-to the rear end of theaircraft to lperform their usual functions. elevatorsmay be.kcont-rolled by ,cablesA Zll. A steering rudder 42'is arranged centrallygof the rear end ofthe apparatus and may be controlled by Cables 43connectedj to ka tiller A pilot or control house 45 is arranged beneath'thebody tiallycentrally thereof and is provided ,with an observationwindow 45* in its forward end; e Afuel tank 46 may be arranged in theThe' of the apparatus substan-A control house and the latter'is providedwith a seat i7v for the operator. `A joy stick i8 is mounted forwardlyofthe drivers seat. rlhis member is movableqin.. one directionto contr-olthe ailerons 37 fand in another directionto controlthe elevat0rs39. -Thestructure and, operation ofthe joy stick is well under-` stood intheartand need not be lreferred to in detail. A steering pedal L9 is connectedto the cables43 in the usualfmanner. f Operation ofthe cables 35 isadapted to be effected by a crank l5() in anydesired manner, lwhilejthecables'3lV are adapted to be operated by a ksecond crank 51..` Y 'f ,lio

As shown in Figures-2 and 4 wheels 5l is operated to swing thecontrolmembers29l to vertical positions, vorto positions wherein thebottoms'of the control members are inclined forwardly. Operation ofthemotor projects air rearwardly into they body or tunnel, and this air isintercepted by thedis- Vttributors As `previously stated, the up` peredges of the distrilfiutors are arranged at progressively increasingheights toward the rear end of the body and each is adapted to interceptthe proper porportion of air according to the weight to .be liftedkatthe bottom portion of the apparatus corresponding thereto. The designofthe distributors and the locations f the upper edgesthereof will, ofcourse, be dependent upon thedis-r tribution of weight carried bytl'ievehicle, and more particularly will depend upon the location of themotor. lt will he understood that the latter may be arranged in the conytrol house if desired, in which oase a smaller proportion of air will beintercepted by the forward distributors. Then the action above referredto takes place, the distributors will cause the air to be projecteddownwardly and rearwardly, while thecontrol members 29 will furtherdeflect the air in asubstaiitially vertical direction thus effecting adirect vertical lifting action. Then the dcsii-edl elevation has beenattainc'ch the joy stl-el; is operated to swing the control members 29rearwardly, whereupon air will be discl'iarged downwardly and.rearwardly The reaction created by the discharge of the air when thecontrol members are arranged vertically will be in a vertical directionto effect direct vertical elevation of the ship, and when the controlmembers are arranged in the solid line position shown in Figure 2, thereVwill be a composite vertical and longitudinal reactionary effectprovided which will sustain the craft and cause it to movelongitudinally. The ailerons are adapted to be operated` in the usualman-ner to provide transverse stability, while the `elevators and rudderare operated to tiltthe craft longitudinally, to eilect steeringthereof. As I'neviouslyvstated, the ailerons are adapted to be operatedin such a manner vthat one `of them will be elevated simultaneously withthe depression of the other, and this action not only stabilizes thecraft but also banks7 the craft when turning. n

The proportion of air lintercepted by the distributors as a whole may bevaried by oper ting the hinged n'ienibers 33. If it is found that thecraft tendsto dip at for ward end, the ineml rs 88 may be swung upwardlyand rearwzlrdly by operating the cranh 50 whereby a. grealer proportionof air willtbe intercepted. by the forward distributors thus effecting agreater lifting action at the forward end of the craft. Similarly, themembers 33 may be swungV downwardly and forwardly to correct too great adipping action at the rear end of the apparatus. TWhile I haveillustrated only the for ward distributors as being provided with themembers 33, it will be obvious that anynumber of the distributors may beprovided with such control means.

The lifting plane 26 serves to effect a lifting action at the forwardend of the craft while traveling in a longitudinal direction,

and the sustaining planes to supple.- ment the vertical; re ction ot thediscl'iargcd air front the dist; utors in iseaining the craft. lt`willbef obvious that when the conH trol niornliers 29 are swungrearwardly inclined posi icalreaetion will be dec on of the sustaii n"planes balai this decrease in verticali 'ng force,

v`The arrangement of the axis of the propeller horizontally and" theplacing of the propeller' in the opening in thc forward' endA of the:tunnell serves to greatlv increase the (gljciency of the opeller bypreventing" lial and longitiu lal"slippage, and yaccordingly theimpelling action of the apparatus described is considerably moreeiiicient than lili ing' action obtained with the usual ielicopterconstructions.

It is to` beunderstood that the forni of the n'tion herewith shown anddescribed is tobcrairen as a preferred'example of the same and thatvarious changes in the shape, size aiufl armani-ement of' parts may beresorted to without departing from the spirit of the invention orv thescope of the subjoined claims.

I' cla-im? l. An aircraft comprising a tunnel having an opening' in itsforward end, a proi'ieller mounted adjacent said opening to im# per airrearwardly into said"` tunnel, ,said tunnel having a horizontallyelongated bottom, 'opening substantially throughout length. for thedischarge of air from said` tunnel', and means for distributing air fromsaid tunnel substantially throughout the area of s d bottoni opening fordischarge therethrough. f

tu aircraft` comprising a tunnel hay ing an opening in its forward end,a propLJe-r mounted adjacent said opening to inipel air rearwardly intosaid tunneh said tunnel having a horizontally elongated bot tomepeningit'or the arge of air fromL said tunnel, means for distributing air fromsaid tunnel substantially throughout the arca' of said bottom oi'ioningfor discharge therethrough, and n cans for controlling the direction ofdischarge of air from said bottoni opening.

3. An aircraft coinprisinna tunnel having anopening in its forward end.a propeller mounted acont said opening to inipel air rearwardly intosaid tunneh'said tunnel having a. horizont-ally elon ated bottoniopening for the discharge of air from said tunnel.v a plurality ofdistributing vanes arranged in said tunnel and adapted to deliect air insaid tunnel downwardly through said bottom opening, and means for controlling the direction of discharge of air from said bottom openilw. i

lill

i'. loi

CIIl

Ll. Pin aircraft comprising a tunnel hav.-l iiig 'an opening in itsforward end, a pro,- pe'ller mounted adjacentsaid opening to inipel airrearwardly ,vinto said tunnel, said tunnel having a horizontallyelongated bottoni opening for the discharge of air froni said tunnel, aplurality of distributing vanes arranged in said tunnel and adaptedgtodefleet air iny said tunnel downwardly through. said bottoni opening,and controlling menibers associated with thelower*extremities of said.distributing vanes for controlling the direction of discharge of airfroin said `bottoin opening. f

An aircraft coinprising a horizontally elongated tunnel krhavingv anopening in its forward end, a propeller arranged in. said opening toiinpel air-rearwardly into said tunnel, said tunnel having a -bottonildischargeopening extending throughout a substantial portion of itslength, and a plurality of distributors mounted in said tunnel andinclineddownwardly and rearwardly, the upper edges of said distributorsbeing arranged at progressively increasing heights toward the rear endof said tunnel, the lower yedges of said distributors being arrangedadjacent said bottoni opening to discharge air therethrough. f

6. An aircraft comprising a horizontally elongatedy tunnel having anopening in its forward end, a propeller arranged in said opening toiinpel air rearwardlyinto tunnel, said tunnel having a bottoni dischargeopening extending throughout a sub-k stantialportion of its length, aplurality of distributors mounted in said tunnel and having their upperedges arranged at progres# sivcly increasing heights toward the rear endof said tunnel, the lower edges of'said f y distributors being` inclineddownwardly and ,rearwardly to discharge air through bottoni opening, andcontrol inenibers pivot-y said ally connected at their upper edges tothelower extremities of said distributors and adapted tocont-rol thedirection of 3lischlargevv rofair froin said bottoni opening.

7. An aircraft comprising a horizontally elongated tunnel having anopeningr in its forward end, a. propeller arranged in said opening-,toinipel 'air rearwardly into said tunnel, said tunnel having a bottoindischarge opening extending throughout a sul,

stantial portion of its length, a pluralityfof distributors inounted insaid tunnel and having their upper edgesgarranged at progressivelyincreasing heights toward the rearl end of said tunnel, the lower edgesof said d iStiibuitors being inclined downwardlyand rearwardly todischarge air through said bottoni opening, control ineinbers ypivotallysaid t connected at their upper edges .to the lower eiitreinitiesofsaid'distrilnitors and adapted' to control the direction offdischarge'ofair from said bottoinopeningx and a pair of longitudinalsiistainingplanes arranged on opposite sides'of said tunnelsubstantially parallel thereto,A l

8. Anaircraft comprising a tunnel having an openingin its forward end, apropeller mounted adjacent saidjopening to inipel air rearwardly intosaid tunnehsaidj tunnel having a horizontally elongated bottoni openfing for the f discharge of air froin said tunnel, plurality of.distributing vaines arranged in saidtunnel and adapted to deflect airin said tunnel downwardly through said bottoni opening,nieans `for,controlling Ather direction ofdischarge of air KVfrom said'bottoniopening, and ineaiis for controlling the proportion of airintercepted'by certain of saiddistributing vanes."

9. An aircraft coinprisinga horizontally elongated tunnel having anopening` in its forward end, a propeller arranged in said opening toimpel air rearwardly `into said tunnel, said ytunnel having a bottonidischarge opening extending th 'oughout asubstantial portion of itslength, a pluralityof distributors mounted in said tunnel and inclineddownwardly andr'earwardly, ythe upn per edges of said distributors beingarranged at progressively increasinglieights ltoward the rear endof saidtunnel, the lower edges Vsaid tunnel and spaced from eachother, saiddistributorshaving their upper edges arranged at progressivelyAincreasing heights toward the rear end of said tunnel, the lowerkportions of said distributors being inclined downwardly randrearwardly, the forward end of said tunnel being provided with acircular opening, a propeller mounted in said opening to iinpel airrearwardly into saidL tunnel whereby it will beproportionatelyintercepted by said distributors. and ineans for varyingthe direction of discharge of air from the open lower portion of said,tunnel` n in testiniony whereof I aiiix iny-signature.

nor e; Doiiiiiinsoii.

said bottoni opening to discharge air

